Airplane wing



Y July 22, 1941. J. l. FrrzuRKA AIRPLANE wma 3 Sh'eets-Sheet l Filed Sept. 18, 1939 Ya." "nllll l INVE'N TOR -A'rToRNEYs WITNESS 3 Sheets-Sheet 2 July 22, 1941.

J. L. FITZURKA AIRPLANE WING Filed Sept. 18, 1939 WITNESS July 22 1941- J. -F1TzuRKA 2,249,729

AIRPLANE WING Filed sept. 1:2,v 1939 ls sheets-sheet s ATTQ RNEYB WITNESS Patented July 22, 1941 UNITED STATES PATENT oFElcE Application september 1s, 1999, serial Nn. 295,493

2 Claims.

The invention relates to airplane wings and more particularly toretractable airplane wings.

The primary object of the invention is the provision of a wing structure of this character wherein the ,wing'surface can be varied for the purpose of increasing airplane speed when in flight, aiding the lifting power and enabling quick take-oil or landing. f

Another object of the invention is the provision of a wing structure of this character wherein the same is novel, being readily actuated, thev mai-n stationary wing or wings being augmented. by adjustable tips thus increasing speed of an airplane when in flight `in relation to the4 carrying load and assuringsafety in landing.

A' further object of the invention is the pro.- vision of a wing structure of this character wherein variance in the effective span of the airplane wing can be had with dispatches conditions may require. I

A still further object of the invention is lthe provision of a structure of this character, which is simple in its makeup, thoroughly reliable and eflicient in operation, susceptible of positive control, convenient for manipulation, ready and easy of adjustment, and inexpensive to manufacture and install.

With these and other objects in view, the invention consists in the features .of construction, combination and arrangement of parts as will be hereinafter more fully described in detail, illustrated in the accompanying drawings, which disclose the preferred embodiment of the invention and pointed out in the claims hereunto appended.

In the accompanying drawings: Figure l is a top plan view of an airplane showing the structural setup of the invention in accordance therewith and associated. with the said plane.

Figure 2 is a transverse sectional view through a stationary wing or sustaining member ofthe plane, being onY an enlarged scale taken on the line 2-2 of Figure 4. A

Figure 3 is a fragmentary horizontal sectional view through the airplane.

on'the line l-l of Figure 1 looking in the direction of the arrows.

Similar reference characters indicate -correspending parts throughout the several views in the drawings. v

Referring to the drawings in detaiLA designates generally the 'fuselage or body portion of an airplane, B the laterally projectedstatlonary wings or flight sustaining members while C is the running or landing gear. I'he fuselage A is equipped with any standard propeller l0 at the Y noseorfront end, and being also equipped with ailerons II elevated at I2 and rudder I3, respectively, these being of conventional type and 011er-,

ated or controlled in any desirable manner.

Each wing. or member B slidably accommodates vin the outermost. end thereof an extensible and retractable tip I4 lwhich increases or decreases the sustaining surface of the airplane in that it augments the said wing or member B. This tip Il is controlled in its movements by dual or twin hydraulic reversing Jacksv including the pair of cylinders I5 arranged in spaced parallel relation within the wing or member B, being fixed therein at I8. Reciprocatingly movable in these cylinders I5 are pistons I1, their stems I8 being carried through packing glands I9 and are pivotally coupled at 2Q tothe inner ends of the said tips I4. Each tip." at the inner 'end thereof has fixed thereto runners 2|, these operating in channeled tracks 22 stationarily built within the wing ormember B at the way 23 provided for the Figure 4 is a perspective view of one of the retractable tips.

Figure 5 is a horizontal sectional view taken through the4 pump. t l

Figure 6 is an'enlarged sectional view taken on the line' 8-8 of Figure5 looking in the direction of the arrows.

Figure 7 is afragmentary front elevation of the plane.

Figure 8 is an. enlarged sectional view taken travel of said tip.

Within the fuselage A is a motor or power -source 2l which through gearing connections 25 operates a pump 26 of the double-acting type. I'his pump is built with valve chests 21 for slide valves 2l which through connecting rods 29 have connection' with a control lever 30 so that said valves will be under manual control for regulating the direction of flow oi' uid through conduits 3|, each having branches 32 opening into the cylindersll at opposite sides of the piston I1 in each jack, and in this manner the travel of the pistons within the cylinders I5is regulated for the extending or retracting of the tips I4 in unison with each other. In other words, the tips Il are'both extended and retracted synchronously and simultaneously with each other.

Each valve chest is fitted with fluid control valves and 3l, respectively, for regulatory flow of fluid from the pump 2l at opposite sides of the piston ll therein, its stem being included in the connections 2l with the motor or power source 24. y

creased speed in night of the airplane in conformity to carrying load and assures safety to the plane while in night and both in taking 0l! or making landings.

What is claimed is:

1. In an aircraft, a fuselage having permanent wings extending laterally on opposite sides thereof,.parallel channel-iron tracks within said wings adjacent the leading and trailing edges thereof, extensible and retractible tips within the outer ends of the wings and having their front and rear edges conforming with the channel-iron tracks in which they freely slide, runners carried by the rear and frontedges of the tips andextending inwardly from the ends thereof and sliding within the channelfirons and forming unbroken continuations of the front and rear edges of the tips, and manually controlled operating means connected to the inner ends of the tips between the runners.

2. In an aircraft, a fuselage having tapered permanent wings extending laterally on opposite sides thereof, parallel channel-iron tracks within said wings adjacent the leading and trailing edges thereof, extensible and retractible tips within the outer ends ofthe wings and having parallel front and rear edges conforming with the channel-iron tracks in which they freely slide, runners carried by the rear and front edges of the tips and extending inwardly from the in-V nner end thereof and sliding within the channelirons and forming an unbroken continuation of the front and rear edges of the tips, andy two manually controlled operating rods connected to the rear ends of the tips adjacent the runners.`

JOHN noms rrrzURKA. I 

